Wings span = 15.3 m Wing area = 27.3 m^2 Take of gross mass = 3900 kg Oswald efficiency factor = 0.9 Zero-lift drag coef
Posted: Fri Apr 29, 2022 9:58 am
Wings span = 15.3 m
Wing area = 27.3 m^2
Take of gross mass = 3900 kg
Oswald efficiency factor = 0.9
Zero-lift drag coefficient = 0.03
Power required to fly at velocity of 300 km/h at an altitude of sea level= 333.61 kW
Thrust required to fly at velocity of 300 km/h at an altitude of sea level= 4003.49 N
Power required to fly at velocity of 300 km/h at an altitude of 4.5 km = 252.56 kW
Thrust required to fly at velocity of 300 km/h at an altitude of 4.5 km = 3030.8 N
Calculate and plot the thrust required and power required curves at sea level and at 4.5 km altitude as the flight velocity is varied from 50 to 500 km/h.
Wing area = 27.3 m^2
Take of gross mass = 3900 kg
Oswald efficiency factor = 0.9
Zero-lift drag coefficient = 0.03
Power required to fly at velocity of 300 km/h at an altitude of sea level= 333.61 kW
Thrust required to fly at velocity of 300 km/h at an altitude of sea level= 4003.49 N
Power required to fly at velocity of 300 km/h at an altitude of 4.5 km = 252.56 kW
Thrust required to fly at velocity of 300 km/h at an altitude of 4.5 km = 3030.8 N
Calculate and plot the thrust required and power required curves at sea level and at 4.5 km altitude as the flight velocity is varied from 50 to 500 km/h.